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An Adaptive Control Method for Shock Sealing of Hypersonic Inlet

An adaptive control, hypersonic technology, applied in high-efficiency propulsion technology, climate sustainability, jet propulsion, etc., can solve the problems of increased weight, reduced reliability, complex actuator structure and control system, etc., to achieve a simple structure. , the effect of easy installation

Active Publication Date: 2022-07-12
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But these methods have also paid a high price: serious weight increase, complex actuator structure and control system, reduced reliability, etc.

Method used

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  • An Adaptive Control Method for Shock Sealing of Hypersonic Inlet
  • An Adaptive Control Method for Shock Sealing of Hypersonic Inlet
  • An Adaptive Control Method for Shock Sealing of Hypersonic Inlet

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Experimental program
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Embodiment

[0021] according to figure 1 Design flow chart of an adaptive control method for hypersonic inlet shock sealing. Obtained by wind tunnel test figure 2 The elastic coefficient required by the medium elastic device, when the flight Mach number and altitude of the aircraft are low, the resistance and the angle of the compression wave system are larger at this time, and the compression surface 2.1 of the intake port will move to the right side in the figure, thereby making the compression wave system hit to the intake port lip cover 2.2; when the flight Mach number and altitude are high, the resistance and the angle of the compression wave system become smaller, and under the action of the elastic device 2.4, the intake port compression surface 2.1 will move to the left in the figure, and make the compression The wave system hits the intake lip cover 2.2. image 3 is the intake port flow field when no adaptive control is performed, at Figure 4 The adaptive control is used to ...

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PUM

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Abstract

The invention provides an adaptive control method for the shock sealing of a hypersonic intake duct. Combined with the characteristic that the resistance of the intake duct gradually decreases during the acceleration of the hypersonic aircraft from a low Mach to a high Mach, an elastic telescopic mechanism is used to realize the compression of the intake duct. The surface moves adaptively with the flight Mach number to achieve the effect of sealing the shock wave system of the intake port under wide-speed flight conditions. Compared with the active control method, the invention does not need external energy input, the structure is simple and convenient for construction and maintenance, and an appropriate elastic coefficient is selected to realize the shock wave sealing effect under wide-speed flight conditions.

Description

technical field [0001] The invention relates to the technical field of hypersonic air inlets, in particular to an adaptive control method for shock sealing. Background technique [0002] Air-breathing hypersonic vehicles rely on themselves to capture air to organize fuel combustion. The hypersonic inlet is an important part of the air-breathing hypersonic propulsion system, and its performance directly affects the working performance of the propulsion system. The flow coefficient of the intake port has the most direct impact on the thrust of the hypersonic propulsion system. The reduction of the flow coefficient corresponds to the same proportional reduction of the thrust of the propulsion system. Therefore, maintaining the maximum airflow capture of the intake port within the aircraft flight envelope is achieved. The key to maximum engine performance. [0003] The hypersonic intake port is usually designed at the operating point of the cruise state. In this state, the com...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/057F02C7/042G01M9/00
CPCF02C7/057F02C7/042G01M9/00Y02T90/00
Inventor 李楠
Owner NORTHWESTERN POLYTECHNICAL UNIV